AH 93-156 (ah93156-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-156 (ah93156-il) Reynolds number: 100,000 Max Cl/Cd: 35.53 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93156-il-100000-n5.txt Download as CSV file: xf-ah93156-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-156
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1933 0.10290 0.09738 -0.0968 0.8869 0.0354
-11.750 -0.1928 0.09847 0.09295 -0.0992 0.8832 0.0350
-11.500 -0.1943 0.09382 0.08829 -0.1017 0.8797 0.0351
-11.250 -0.1991 0.08892 0.08343 -0.1042 0.8756 0.0356
-11.000 -0.2068 0.08342 0.07796 -0.1073 0.8716 0.0360
-10.750 -0.2171 0.07728 0.07184 -0.1110 0.8677 0.0358
-10.500 -0.2435 0.06760 0.06216 -0.1180 0.8631 0.0353
-10.250 -0.2772 0.06052 0.05496 -0.1213 0.8574 0.0344
-10.000 -0.3048 0.05603 0.05029 -0.1210 0.8524 0.0346
-9.750 -0.3299 0.05254 0.04660 -0.1186 0.8477 0.0343
-9.500 -0.3500 0.05014 0.04401 -0.1148 0.8427 0.0346
-9.250 -0.3635 0.04742 0.04099 -0.1114 0.8385 0.0349
-9.000 -0.3717 0.04464 0.03785 -0.1082 0.8352 0.0354
-8.750 -0.3763 0.04218 0.03504 -0.1049 0.8307 0.0358
-8.500 -0.3758 0.03979 0.03226 -0.1020 0.8269 0.0363
-8.250 -0.3705 0.03748 0.02948 -0.0994 0.8238 0.0371
-8.000 -0.3606 0.03547 0.02695 -0.0971 0.8211 0.0385
-7.750 -0.3440 0.03443 0.02586 -0.0960 0.8184 0.0400
-7.500 -0.3297 0.03358 0.02487 -0.0944 0.8145 0.0416
-7.250 -0.3129 0.03237 0.02342 -0.0931 0.8114 0.0433
-7.000 -0.2931 0.03105 0.02180 -0.0919 0.8088 0.0450
-6.750 -0.2711 0.02989 0.02035 -0.0911 0.8065 0.0475
-6.500 -0.2485 0.02904 0.01949 -0.0906 0.8045 0.0501
-6.250 -0.2303 0.02846 0.01882 -0.0894 0.8009 0.0528
-6.000 -0.2106 0.02781 0.01801 -0.0882 0.7975 0.0556
-5.750 -0.1900 0.02715 0.01730 -0.0873 0.7946 0.0593
-5.500 -0.1682 0.02661 0.01674 -0.0865 0.7921 0.0637
-5.250 -0.1442 0.02600 0.01598 -0.0858 0.7900 0.0686
-5.000 -0.1221 0.02542 0.01543 -0.0851 0.7881 0.0747
-4.750 -0.1110 0.02544 0.01542 -0.0827 0.7832 0.0807
-4.500 -0.0942 0.02513 0.01514 -0.0811 0.7796 0.0880
-4.250 -0.0737 0.02477 0.01476 -0.0800 0.7769 0.0990
-4.000 -0.0513 0.02436 0.01437 -0.0791 0.7747 0.1139
-3.750 -0.0279 0.02392 0.01400 -0.0785 0.7730 0.1366
-3.500 -0.0216 0.02414 0.01435 -0.0754 0.7670 0.1594
-3.250 -0.0050 0.02389 0.01430 -0.0738 0.7634 0.2057
-3.000 0.0141 0.02337 0.01420 -0.0726 0.7608 0.2932
-2.750 0.0304 0.02259 0.01403 -0.0706 0.7587 0.4373
-2.500 0.0848 0.02288 0.01563 -0.0717 0.7583 0.7596
-2.250 0.0780 0.02370 0.01642 -0.0655 0.7518 0.8017
-2.000 0.0800 0.02423 0.01685 -0.0606 0.7470 0.8364
-1.750 0.0991 0.02464 0.01712 -0.0581 0.7445 0.8643
-1.500 0.1269 0.02493 0.01725 -0.0571 0.7427 0.8869
-1.250 0.1623 0.02541 0.01761 -0.0581 0.7399 0.9054
-1.000 0.2661 0.02542 0.01735 -0.0713 0.7418 0.9268
-0.750 0.3072 0.02604 0.01791 -0.0747 0.7364 0.9432
-0.500 0.3662 0.02602 0.01777 -0.0810 0.7341 0.9531
-0.250 0.4032 0.02595 0.01761 -0.0832 0.7311 0.9597
0.000 0.4391 0.02577 0.01732 -0.0851 0.7288 0.9630
0.250 0.4729 0.02550 0.01696 -0.0863 0.7269 0.9662
0.500 0.4839 0.02617 0.01765 -0.0846 0.7190 0.9719
0.750 0.5147 0.02610 0.01753 -0.0857 0.7155 0.9747
1.000 0.5475 0.02586 0.01722 -0.0868 0.7130 0.9771
1.250 0.5805 0.02555 0.01686 -0.0878 0.7111 0.9792
1.500 0.5872 0.02645 0.01780 -0.0855 0.7018 0.9844
1.750 0.6187 0.02625 0.01757 -0.0865 0.6989 0.9863
2.000 0.6525 0.02590 0.01720 -0.0876 0.6967 0.9879
2.500 0.6889 0.02658 0.01793 -0.0858 0.6842 0.9944
2.750 0.7229 0.02621 0.01755 -0.0869 0.6819 0.9958
3.250 0.7523 0.02686 0.01827 -0.0837 0.6687 1.0000
3.500 0.7807 0.02645 0.01786 -0.0835 0.6664 1.0000
4.000 0.7850 0.02716 0.01864 -0.0753 0.6521 1.0000
4.500 0.7799 0.02776 0.01928 -0.0653 0.6373 1.0000
5.000 0.7766 0.02833 0.01989 -0.0559 0.6222 1.0000
5.500 0.7564 0.02970 0.02131 -0.0448 0.6018 1.0000
6.000 0.7932 0.02900 0.02067 -0.0410 0.5921 1.0000
6.250 0.7816 0.02992 0.02161 -0.0357 0.5800 1.0000
6.500 0.8108 0.02916 0.02089 -0.0352 0.5771 1.0000
6.750 0.8058 0.03007 0.02185 -0.0310 0.5651 1.0000
7.000 0.8379 0.02925 0.02107 -0.0309 0.5620 1.0000
7.500 0.8621 0.02993 0.02185 -0.0270 0.5433 1.0000
7.750 0.8807 0.02999 0.02199 -0.0258 0.5345 1.0000
8.000 0.8971 0.03028 0.02233 -0.0246 0.5250 1.0000
8.250 0.9271 0.02972 0.02184 -0.0244 0.5182 1.0000
8.500 0.9416 0.03020 0.02239 -0.0231 0.5070 1.0000
8.750 0.9714 0.02972 0.02198 -0.0230 0.4988 1.0000
9.000 0.9930 0.02979 0.02210 -0.0222 0.4880 1.0000
9.250 1.0102 0.03017 0.02256 -0.0212 0.4759 1.0000
9.500 1.0318 0.03029 0.02274 -0.0205 0.4640 1.0000
9.750 1.0553 0.03030 0.02279 -0.0199 0.4518 1.0000
10.000 1.0764 0.03047 0.02299 -0.0192 0.4384 1.0000
10.250 1.0950 0.03082 0.02337 -0.0183 0.4244 1.0000
10.500 1.1094 0.03145 0.02404 -0.0171 0.4095 1.0000
11.000 1.1298 0.03328 0.02593 -0.0142 0.3771 1.0000
11.250 1.1359 0.03449 0.02716 -0.0125 0.3594 1.0000
11.500 1.1410 0.03580 0.02848 -0.0109 0.3407 1.0000
11.750 1.1454 0.03719 0.02987 -0.0093 0.3214 1.0000
12.000 1.1485 0.03874 0.03137 -0.0077 0.3014 1.0000
12.250 1.1498 0.04054 0.03317 -0.0062 0.2807 1.0000
12.500 1.1504 0.04246 0.03504 -0.0048 0.2598 1.0000
12.750 1.1502 0.04457 0.03710 -0.0036 0.2386 1.0000
13.000 1.1490 0.04687 0.03935 -0.0024 0.2175 1.0000
13.250 1.1466 0.04937 0.04178 -0.0014 0.1968 1.0000
13.500 1.1437 0.05207 0.04443 -0.0005 0.1753 1.0000
13.750 1.1393 0.05503 0.04731 0.0002 0.1555 1.0000
14.000 1.1358 0.05803 0.05030 0.0007 0.1354 1.0000
14.250 1.1305 0.06134 0.05354 0.0011 0.1173 1.0000
14.500 1.1247 0.06484 0.05699 0.0013 0.1014 1.0000
14.750 1.1194 0.06839 0.06052 0.0013 0.0866 1.0000
15.000 1.1135 0.07215 0.06426 0.0011 0.0745 1.0000
15.250 1.1068 0.07612 0.06822 0.0008 0.0652 1.0000
15.500 1.1022 0.07995 0.07210 0.0003 0.0575 1.0000
15.750 1.0966 0.08399 0.07618 -0.0003 0.0514 1.0000
16.000 1.0913 0.08810 0.08034 -0.0011 0.0469 1.0000
16.250 1.0863 0.09223 0.08455 -0.0021 0.0429 1.0000
16.500 1.0827 0.09626 0.08868 -0.0031 0.0396 1.0000
16.750 1.0760 0.10079 0.09322 -0.0044 0.0370 1.0000
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Polar data table (+)
Polar graphs
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